Abstract
The aeroelastic characteristics of a wing with control surface freeplay are investigated. The transonic small disturbance equation is used for unsteady aerodynamic forces in subsonic/transonic region. The fictitious mass method is introduced to apply a modal approach to nonlinear structural models. Nonlinear aeroelastic time responses are calculated by the coupled time integration method. Using these methods, an efficient aeroelastic analysis is achieved for aerodynamic and structural nonlinearities simultaneously. The effects of the aerodynamic nonlinearity, initial flap amplitude, and freeplay magnitude in aeroelastic characteristics are investigated in this study. 섂 돀좽?⨀ 塨?⨀ 炏?⨀ 餂 돐 졠잖⨀ 䡙잖⨀ 颏?⨀ 뤁 뎀 ／ࠀ?⨀ 礁 덐 态 Ȁ 顲ꂪ ᡳꂪ Āā? 뤀 댐?⨀ ޚ䜄 僈?⨀ 䀠 ゾ?⨀ 䂾?⨀ Ă 逐 煥獣愠獵扨敡瀀 ｿｿｿｿ 壑?⨀ 壑?⨀ ꤠ 돀좽?⨀ 塨?⨀ ࠏ?⨀ 脠 돐 ꡙ잖⨀ ꡙ잖⨀ 』?⨀ 夠 뎐 ／ࠀꡢ잖⨀ 愁 덀 态 Ȁ �嚛 研嚛 Āā?
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